Subsonic Maneuver Capability of a Supersonic Cruise Fighter Wing Concept
Subsonic Maneuver Capability of a Supersonic Cruise Fighter Wing Concept
- New search for: G. D. Riebe
- New search for: C. H. Fox
- New search for: G. D. Riebe
- New search for: C. H. Fox
A theoretical and experimental investigation was conducted of the subsonic maneuver capability of a fighter wing concept designed for supersonic cruise. To improve the subsonic maneuver capability, the wing utilized full-span leading- and trailing-edge flaps that were designed with the aid of a subsonic-analysis computer program. Wind-tunnel tests were made at Mach numbers of 0.3, 0.5, and 0.7. Force and moment data obtained were compared with theoretical predictions of Mach 0.5 from two subsonic-analysis computer programs. The two theoretical programs gave a good prediction of the lift and drag characteristics but only a fair prediction of the pitching moment. The experimental results of this study show that with the proper combination of leading- and trailing-edge flap deflections, a suction parameter of nearly 90 percent can be attained at a Mach number of 0.5 and a lift coefficient of 0.73; this is a three-fold improvement from 30 percent for the basic wing.
Document information
Subsonic Maneuver Capability of a Supersonic Cruise Fighter Wing Concept
1987
74 pages
Report
No indication
English
Aircraft , Aerodynamics , Fighter aircraft , Supersonic cruise aircraft research , Maneuvers , Subsonic speed , Wings , Aerodynamic coefficients , Computer programs , Drag , Flaps (Control surfaces) , Leading edge slats , Lift , Mach number , Pitching moments , Predictions , Supersonic airfoils , Trailing edge flaps , Wind tunnel tests
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